Altitude-Based Fuel Temperature Control for Gas Turbine Engines
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Solution Overview
Problem
Traditional thermal management systems in gas turbine engines fail to protect fuel hardware from contamination and lacquer build-up, particularly at low altitudes due to high oxygen content and elevated fuel temperatures, which affects fuel efficiency and engine performance.
Innovation Solution
A thermal management system that determines the current altitude of an aircraft and adjusts the fuel temperature of the gas turbine engine, scheduling a lower temperature at lower altitudes to prevent deposit formation and an elevated temperature at higher altitudes to enhance fuel efficiency and engine performance, while also managing oil temperatures to prevent heat exchanger overload.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If fuel temperature is elevated to improve fuel efficiency and engine performance, then engine performance is improved, but fuel hardware experiences contamination and lacquer build-up
Solution Approach 1:
The patent applies dynamics by making the fuel temperature control system adjustable and responsive to operating conditions. The thermal management system dynamically modifies fuel temperature based on altitude and operational parameters, transitioning from a static temperature control approach to a dynamic one that adapts to changing flight conditions, thereby resolving the contradiction between maintaining high temperature for performance and low temperature to prevent deposits.
Solution Approach 2:
The patent changes the temperature parameter of fuel based on altitude and operational conditions. By modifying the fuel temperature parameter dynamically - maintaining lower temperatures at low altitudes to prevent lacquer formation and allowing higher temperatures at high altitudes for optimal performance - the system resolves the contradiction between engine performance and fuel hardware protection.
2Reliability
If fuel temperature is reduced to prevent deposit formation on fuel hardware, then fuel hardware is protected, but fuel efficiency and engine performance decrease
Solution Approach 1:
The system dynamically adjusts fuel temperature based on real-time altitude and operational data. Rather than maintaining a constantly low temperature, the system transitions to dynamic control that raises fuel temperature when altitude and conditions permit, thereby maintaining hardware protection while recovering fuel efficiency and performance benefits.
Solution Approach 2:
The patent implements parameter changes by adjusting fuel temperature based on altitude thresholds and operational modes. The system changes the temperature parameter from a consistently low state to a variable state that increases with altitude, resolving the contradiction between hardware protection and fuel efficiency through conditional parameter modification.
3Device complexity
If a single fuel temperature is maintained for all operating conditions, then system complexity is reduced, but both fuel hardware protection and fuel efficiency cannot be optimized simultaneously
Solution Approach 1:
The patent introduces dynamic control capabilities to the thermal management system, enabling it to respond to changing operational conditions. By implementing altitude-based temperature modification and continuous monitoring, the system transitions from a simple static control approach to a dynamic one that optimizes both hardware protection and fuel efficiency without excessive complexity.
Solution Approach 2:
The system implements parameter changes based on altitude and operational conditions, modifying fuel temperature from a fixed single value to a variable parameter that adapts to flight conditions. This resolves the contradiction by allowing the system to maintain hardware protection at low altitudes while improving fuel efficiency at high altitudes, achieving dual optimization through conditional parameter adjustment.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The system effectively protects fuel hardware from lacquering and deposit formation at low altitudes while optimizing fuel efficiency and engine performance by varying fuel temperatures based on altitude, and ensures oil temperature remains within safe limits, thereby improving overall engine operation.
Implementation Method 1
Heat may be transferred into the engine fuel in order to increase fuel efficiency and engine performance
Data Source
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AI summary
A method of protecting fuel hardware for a gas turbine engine in an aircraft is disclosed. The method may include determining a current altitude of the aircraft, and controlling a temperature of fuel for the gas turbine engine based at least in part on the current altitude. A thermal management system for a gas turbine engine in an aircraft is also disclosed. The thermal management system may include a sensor configured to detect a current altitude of the aircraft, and a controller in operative communication with the sensor. The controller may be configured to manage a fuel temperature for the gas turbine engine based at least in part on the current altitude detected by the sensor.